US988039A - Airship. - Google Patents

Description

J. JV. sILAvIN.

AIBSHIP. APPLIoATIoN FILED 001228. 190s.

Patented Mar.2s,1911.

' a SHEET s-s'HEnT 1.

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J. J. SLAVIN.

AIRSHIP.

' Arfmoulox FILED 0012s, 190s. 988,039.

3 SHEETS-SHEET 2.

Patented Mar. 28, 1911.

J. J. SLAVIN.

AIRSHIP. APPLICATION FILED 001223. 190B.

Patented Mar.28, 1911.

3 SHEETS-SHEET 3.

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f. En s'rnans rafrnnaforrron JAMES J'. SLAVIN, OF-LOS ANGELES, CALIFORNIA'.

AIRSHIP.

Specification of Letters Patent.

Patented Mar. as, i911.

Application led ctober 28, 1908. Serial No. 459,938.

To all whom 'it may concern:

Be it knownvthat I, JAMES J. SLAviN, a citizen of the United States, residing at Los Angeles, in the county of Los Angelesl and State of California, have invented new and useful Improvements in Airships, of which the following' is a specification.

'This inventionV relates to air-ships and more particularly to air-ships of the heavier than air object to provide an organized air-ship, particularly with the object of obtaining stability of the same in air-supported condition and under all circumstances tending to affect the same with 'respect to stability, such as varying air pressure and variation in the 4disposition ofthe load. With this object particularly in view I provide means for producing,maintaining and conserving stability which in their operation are substantially automatic, the condition of stability being, 'in its produc-tion, maintenance and conservation, responsive to the action of said means which latter -in turn are delicately Vand definitely responsive to variation of working conditions and positions and the A supported load.

conditions of the vsupporting .medium and heretofore produced and In air-ships as with varying successful operation, a general requirement` has existed that stability be maintained by predetermined action ofthe o erator or navigator, such as the applicat1on of specific'lmeans or mechanism, or .the variation of the position of the load of the airship. I

It is the primary object of'this invention to obviate the necessity of such specific control of the air-ship by human supervision; and to that end I 'provide certam means,

`mechanism and combination of parts, ele-' ments and features, which cooperate and in- /ter-operate to the accomplishment of automatic control and regulation.

With the above and other objects in view, the invention consists in the provision, construction, association, combination and rela-4 tive arrangement of parts, members and features, all as hereinafter`described, shown in the accompanying drawings and finally pointed out in claims.

In the drawings Figure 1 is a fragmentary side elevation, Vpartly in'longitudinal section and partly broken away for clearness of'illustration, of an air-ship embodying'the features ofthe invention; .Fig.

type; and it has for itsA or deflecting vmembers to Y stability,

2 is a top planview ofthe same, parts being omitted and parts being brokenA away for clearness of illustration; Fig. 3 is a side elevation Aupon an enlarged scale, and partly sectioned and broken away for clearness of.

illustration, of certain essential features of the invention; Fig. 4 is a top plan view, partly longitudinally. sectioned, and parts Vbeing omitted for -clea-rness of illustration, -of the construction shown iuFig. 1; and,

Fig. 5 is a top plan view, partly broken away for clearness of illustration, of `a modified form of construction, the same including,

' in combination certain of the other features and elements shown in the other figures and has certain additional features andelements for operation and utilization in association with or without the aforementioned fea? tures and elements.V

Corresponding parts in all the figures are denoted by the .same reference characters.

Referring with particularity to the `drawings and to Figs. l to 4: ofthe same, Vinelusive, the improved air-ship comprises in the main, a body A, supporting or defiecting members B for the body, and means C controlling and regulating the supporting B and whereby'the latter are inter-related. The body A is, in practice, properly organized for the reception of the load and motor and the con'- venience of the operator, such featuresbeing omitted in the drawings for better illustration of the working parts.v According to the invention the controlling means C comtwo separate members or organisms a and eratively combined 'with'the supporting or .deflecting members B` and each of which, according .to its specific nature and functions, as hereinafter set forth, controls the' tained. The supporting or deiiectn memb, respectively, both of which' are op'- bers B, each of which is illustrate as an .aeroplane lo, 'are thus operatively connected i through the*V a ency of the operative connections D, and v our of such supporting or deflecting members are 'illustrated as em in the particular embodiment of the tion shown in the drawings,

Invenward pairs e, the membersof each of which A pairs are arranged in a plane transverse of v ditions of the air,

the longitudiua plane of the air-ship, said aeroplanes of each pair of the same being disposed at the respective sides of the central longitudinal plane of the air-shii. It thus results that an aeroplane is provi ed at each ofthe four corners of the air-ship, speaking in general terms, so that said aero-V planes may ]ointly and severally operate to cause the supporting and balancing of the entirety at four points, two of which are forward, and two rearward of the center of the body A. f

. 'lhe member or organism a of the `control ling means 'C performs the function of establishing and maintaining stability and l equilibrium of the entire air-ship in opposition to varying or relatively varying conconstituting the supporting medium.; while the member or organism b of the controllin means function of establishing and stability and equilibrium of the relation, more particularly, to shifting of the load of the air-ship. The members or maintaining organisms a and b vboth preferably perform -their functions through the agency of pneumatic or hydraulic means, or both, the former of which includesan air-receiver or container f. Variations in the conditions afecting the aeroplanes c, or any of the same, are caused to affect all of the aeroplanes in such manner that stability is established and maintained through the agency of such neumatic or hydraulic means and the memser or organism a of the controlling means C. Variations in the dispositions of the load upon the body A affect the condition of the member or organism b of the controlling means C which latter, in turn, affect the aeroplanes c to establish and Amaintain stability. The member vb of the controlling means, in' the construction illustrated, includes a gyroscope g which is associated with the pneumatic or hydraulic means above referred to, in its control of the aeroplanes c, as described. The particular nature of-the pneumatic and hydraulic means,' as -employed, will be hereinafter set forth. i Referring now to Fig. A5, an air-ship is illustrated embodying the features ofthe in.

vention heretofore described, and supported by lateral supporting members E, which are disposed, respectively, laterally of the body F of the air-ship. In th' tion, the parts, elements and features above recited, and shown in Figs. 1 to 4, inclusive,

yare provided; the same vbeing designated by loyed said aeroplanes y being grouped in forward pairs d and rear- C performs the t air-'ship with lmension of each of said Y tirety.

is form of construc-l the same reference characters, as` employed in connection with the other figures. TheA operative connections for the members e, the latter comprising each an aeroplane 71.-, are specifically separate andv distinct. 70 A particular preferred form of` provision, construction, combination, association land relative arrangement of parts, members and features, of an air-ship embodyingthe features of the invention, is as follows The 75 laeroplanes o in theirrespective forward and rearward pairs, are lirinly supported, and connected with the body A, by the frame member or members 6. ranging' longitudinally of the air-ship. The particularjlocation of the aeroplanes c, with respect to their distancefrom the body A, is'a matter to be predetermined -upon consideration of the vworking conditions and the requirements.v of the air-ship. The dimensions and propor- Y tions of the aeroplanes c are correspondingly to be predetermined. For each aeroplanes, oppositely directed sleeves are fixed to the frame member 6, as at 7 8 designating each of said sleeves, which, as illus trated in Fig. 4, may be united in continuous formation. Each of the aeroplanes is pair of the which the aeroplane is vrigidly fixe the innerend ofeach of said shafts is received within one of the sleeves 8, and'so accommodated vtherein as to freely rotate. Each of the aeroplanes c is preferably rectangular inform, and the shaft 9 which supports each of the same is. preferably arranged nearer` to the forward edge portion 10 of the aeroplane than to the opposite or rearward edge portion, thus supporting the aeroplane eccentrically; and the greater diaeroplanes is prefair-ship as anenprovided with a transverse yshaft 9 upon constituting an auxiliary cylinder 12 com'- municating with the cylinder 11v which latter extends horizontally whenthe air-ship is in proper equilibrium.' The cylinder 11 is di' vided into upper and lower chambers, 1la and 11b, respectively, by a horizontal transverse path or partition 13, the end portions of which arespaced from the end portions of.- the cylinder to permit communication between the chambers 11a and 11". The lower 130 17, respectively, both of which range longitudinally of the air-ship, lthe former ranging forwardly and the latter ranging rearwardly and being connected at their outer ends with, and embodied in, the operative connections D. The cylinder 11 is provided with detachable cylinder heads 18, each of which has a stuffing box 19, accommodating the respective piston rod 16 or 17. Within the auxiliary cylinder 12 is mounted a'piston 20, having a stem 21 which passes slidably through a guide 22 to maintain alinement of the piston within the cylinder; the cylinder 11, with the exception of the spac Figs. 1 and 4, such Huid being of a low degree of elasticity of compressibility, such as water, gasolene, or vegetable or mineral oils;

.and the weight of such mass of liquid is disposed upon the lower walls of the cylinder 11 and upon the piston 20 within the cylinder 12.' The normal spacing or relative separation of the pistons 14 and 15 is determined bythe position of the piston 20 within its cylinder; such piston determining the height of the column ofliquid within the cylinder 12. To regulate these conditions, I provide controlling means m associated with the pneumatic means employed and comprising a connecting pipe 23 extending between the lower portion of the cylinder 12 and the air container f, said pi e being controlled by valve or cock 24. gy admission of a further quantity of compressed air to the cylinder 12 beneath the piston 20, the

latter may be elevated and the pressure of the same -upon the fluid within the cylinder 11 and the upper portion ofthe cylinder v12 will cause the elevation of a portion of fluid from the cylinder 12 into the cylinder 11 and the consequent relative approach of the plstons 14 and 15. The controlling meansm may also include an exhaust valve or cock 25, whereby compressed air may be released from the consequent relative lseparation of the pistons 14 and 15.A

The member b of the controlling means C comprises four cylinders 26, 27 28 and 29,

respectively, which are supported by 'the frame of the body A, being illustrated as connected with the cylinder- 11, as at 30, at

the inner end of-each of the same. Said cylinders are arranged in pairs, two of which are disposed at the forward portion of the body, the remaining two being disposed at- -the rearward portion of the body; and each of said cylinders is provided with a separate piston, 31, 32, 33 and 34, respectively, which pistons operate longitudinally of the body A; the cylinders` 26 to 29, inclusive all` ranging longitudinally of the body, and two being disposed at each side of the longitudinal plane of the body. The cylinders 26 and 27 are connected by a web or flange 35, at their upper outer ends; and the cylinders-28 and 29 are similarly connected by a web or iange l36. Each of the webs or Viianges 35 and 36 is formed into or provided with a'bearing 37; and through each of said bearings plays one of the piston rods 16 and .17. The said piston rods are thus caused to act in proper alinement. Through the agency of theremaining features of the controlling means C andthe operative connections D, each of the pistons 31 to '34, in-

elusive, is operatively connected with one and all of the aeroplanes 0. To this end, each of the pistons 31 to 34, inclusive, is provided with a separate piston rod, 38, 39, 40 and 41, respectively; the piston rods 38 and 39 ranging longitudinally of the air-ship and forwardly, and the piston rods 40 and 41 ranging longitudinally of the air-ship and rearwardly. Outwardly of the cylinders 26 and 27, the piston rods 38 and 39 are' oonnected with the forward end portion of the piston rod 16 through the agency of the connecting lever 42, centrally pivotally connected, as at 43, with the forward end por- `tion of the piston rod 16, and provided with elongated end slots 44 receiving pins 45 projectingl respectively from the forward end portions of the piston rods 38 and 39. Each of the shafts 9 of each of the forward aero.-

planes o is provided, inwardly respectively of the aeroplanes, and in alinement with the respective piston rod 38 or 39, withan upwardly projecting arm 46 having predetermined angularity with respect tothe body plane of the rrespective aeroplane; and each of said `,arms 46 is pivotally connected, as

at 47, at its upper end, with' a link arm 48 which is likewise pivotally connected as at 49, with the respective piston rod 38 01'139.

Both of Vthe piston rods 40 and 41 are connected with the piston rod 17 through the agency of a connecting lever 50 which is centrally pivoted, as at 51, in connection with thel rearward end portion of the piston rod 17 of the said connecting lever 50 being .provided with elongated end slots 52 receiving pins 53 projecting respectively from the piston rods 40 and41. Each of the shafts 9 of the rearward aeroplanes c is provided withv a downwardly directed arm 54- extending at predetermined angularity with respect to vthe body plane'of the Vrespective aeroplane; and each of said arms is connected at its outer end with the adjacent end portionbf the alined piston rod 40 or 41 by v movement of each and all of the others .of

a link arm 55 pivotally connected at one end,

movement of either of the pistons -14 and 15 within the cylinderll, will be accompanied by movement ofthe other piston and movement of all of the four aeroplanes; and that likewise movement o f any one of the istons 31 to 34, inclusive, will be accompanled by said pistons and movement' of all. of the aeroplanes c, vand b of the controlling means C are interzdependent and jointly operative through the agency of the operative connections D, to

the end that all of the aeroplanes are af fected as to their operative positions of angularity through the operation of each of the members a and b.

Referring now to the member` or organism l b, the. controlling means C, including the gy- 5 roscope g,

` tively, which the sainev comprises four upright tubular supports58,'59, 60 and'61, respecprojectupwardly from the air container f. The uprights 58 to 61, inclusive, are arranged in an equall spaced group, in

which said supports are dlsposed at the lfoul" corners of a square. Between the outer end portion of each of the cylinders 26 tov29, in` elusive, and the air container f, at points adjacent to the respective supports 58, 59, 60 and 61, extends a separate air connection pipe 62. Y i

The frame .63 of the gyroscope g is provided at its smaller andupper end portion with an upwardly projectlng conical bear# ing head 64, which is mounted fof' oscillat1on or universal movement in a bearing or the upper portion of each of said .tubular which is in turn ,55 posed beveled gears 72 and 73, respectively,

76 `and 77,

seat 65 su ported at the opposed innerl corners 660i) rectan lar frames 67, leach of which is connect as at`68, at the corner diametrically opposite the c0rner 66,. with one of the tubular uprights 58 to 61, inclusive, as best illustrated'in Fig.' 3. Within uprlghts is'mounted ashort shaft 69, fixed therein, as at 70, against rotation; rotatably mounted upon the shaft 69 above the upper end of the respective upright, is a collar 71,

fixed to the lower of opwhich are loosel 69. -Meshing with 73 are two beveled tively, the axes of right angles each to mountedfupon the shaft both of said gears 72 and gears 74 and 75 respecwhich are arranged at the other, each of said outer ends respectively of horizontal shafts n respectively, which extend through tubular members of, the adjacent frame 67; a separate pair of shafts 76 and 77 is provided for each of the pairs of bevthus,'both of the membrs'af leled. gears l74 and 75. Loosely mounted Aupon the shaft 69 above the upper beveled mutilated or segmental ratchet 79 arranged a vertical shaft 82 which is' .the collars 71 and 78 is provided 4 beneath a collar 85aiXed to the sha-ft 82 is ea collar 85; and fixed to the shaft 82 laterally of the ratchet 80 is a collar 86, above the collar 85a. and 86, respectively opposite the ratchets 79 and 80, *projects a tubular housing 87 'and 88, respectively, for a separate pawl or pin 89 and 90, respectively, whichlpawls or pins respectively operate in connection with the ratchets 79 and 80. vWithin each` of the housings 87 and 88 is disposed a coil spring 91 tending to force the respective pawl or pin outwardly or into engagement with the respective ratchet. As the beveled gears 72 and 73 rotate in opposite directions, under the drive'of the beveled gears 74 and 75, the ratchets 79 and 80 are oppositely driven, and said ratchets are formed so that the pawl 89 or 90 of each rides overthe 'same without rotating the-respective collar 85 or 86, upon rotation of the shaft 76 or 77 to cause the beveled gears 72 and 73 to operate each in one direction; and whereby, oppoeach of said pawls is caused to rotate lts collar upon the rotation' of the shaft 76 or 77 inan opposite direction, in each case, to that above stated. The ratchet 80 and its From each of the collars 85 v pawl 90 cause therotation of the shaft 82 i in one direction; and the ratchet 79 and its' lpawl 89 cause the rotation of the collar 85 in the opposite direction.

v As above'stated, durlng the operation of each of the pawls 89 and 90 vto rotate the collar 85l or the collar 86, the other of said pawls moves inoperatively over the face of its ratchet. .I

The above description concerns but one of the shafts 82 and the attendant parts, together with one of the shafts 76 and one lof the shafts 77 for oppositelyrotating two of the beveled gears 72 and. 73. It is to be understood that there are four setsl or groups of such parts and f iatures, one separate set V being associated with each of the tubular uprights 58 to 61, inclusive. There are fourl of the shaftsA 76 and 'four of the shafts 77. Each of the shafts 76 isprovided at yone end.v with a beveled gear 74 meshing with-one o-f the beveled gears 72 and one of the beveled gears 73; and each of the shafts 77 is provided at one end with a beveled gear 75 'meshing with one ofthe beveled gears 72 and one of the beveled gears 7 3.

The shaft 82 in each of the four installations of the same, controls the admission of air from the container f to the respective ,l connection pipe 62, through the agency of a suitable valve 91 atV the lower end of such shaft 82. In connection with the collar 85l mounted loosely upon the shaft 82 and projecting laterally therefrom, is an arm 92, which is pivotally connected at its outer end, as at 93, with a connecting rod 94, which is likewise. pivotally connected, as at 95, with the outer end of an arm 96 vcontrolling an exhaust valve 97 of any preferred form arranged at the outer end portion. of the re- .container f to the outer end of the cylinder,

' 26 to 29, inclusive, respectively which cylin- 26 to 29, inclusive. -From the collar 85 pro-l extend between the outer end portions ofder is diagonally opposite to such valves and the shaft 82, controlling thesame,1as clearly illustrated in Figs. 2 and 4. n

From the above description it fs manifest that lrotation of each vertical shaft 82, namely in that direction indicated by the respective arrow, in Fig. 2, will-.admit air from the container f to the respective connection pipe 62 and to the outer end portion of the respective cylinders 26 to 29, inclusive; and

.that rotation ofthe collar 85 in the opposite direction will operate to open the respective exhaust valve 97 and permit the escape of compressed air from ythe respective cylinder jects a lateral'arm 98; and opposite from the collar 86 projects laterally an arm 9 9. Contractile springs 100 and 101, respectively,

the arms 98 and 99 land the adjacent frame 67, or other convenient point Iof attachment. Said springs normally tend to rotate the collars 85 and 86, respectively/,in

.opposite directions to maintain the admission valve 91 closed and the exhaust valve 97 open. The collar`85 acts upon the valve 97 through the connecting rod 94 andthe collar 86 acts upon the valve 91 through the shaft 82.

A plurality of sets, four in number, of mutilated ratchet gears 102, two in each4 set, are mounted respectively between the frames 67, in alternation therewith, upon short shafts 103 fixed in the sides of said frames;

and each of said gear heads is provided with an inwardly directed arm 104; the end portion of which is loosely accommodated in a separate socket bearing 105 fixed to the upper yportion of the conical bearing head 64. Said arms and their bearings 105 are in adjacent sets of the same, separated by angles of 90. Each of `the gear heads 102 meshes with a separate pinion 106 rotatably mounted in pairs upon separate short shafts 107 supported by two of the frames 67 and each of said pinions 106 meshes with a. separate gear 108, two of which are xed, respectively to the opposed ends of shafts 76 and 77, of two of the sets of gears 74 and 75. Each of the pairs of gears 108 is arranged in an open space between two of the frames 67, wherein one of the pairs of gear heads 102 and one of the pairs of pinions 106 are accommodated. Two of thel arms 104, as. shown in Fig. 2, are preferably longer than the other two of said arms, being opposed ,arms 104. And to vaccommodate such extra length, the pinions 106 and the shafts 107 of the same are omitted with respect to the groups of elements including such longer arms 104. The purpose of such construction and arrangement will hereinafter be pointed out. Contractile springs 108a tend-to hold the ends of the arms 104 in engagement with vtheir socket bearings 105. To cause operation of the rotatingv or spinning member 109 of the gyroscope g, which is suitably Amounted within the frame 63,.the shaft 110 of the same is provided with a plurality of buckets or `blades 111 against which a motive medium may be projected by operating means o whichin the present instance comprises a exible air pipe 112 connected at its discharge end with the frame 63 of the gyroscope and extending to a valve 113 through which air may be admitted to the pipe 112 from the container f.

Referring now to the modified form. of construction, shown in Fig. 5, the same may be organized partially or completely n toto to conform with the construction and arrangement herein above described,v

and shown in the other figures. In addition l to such construction and arrangement, however, the body F comprises .a shell or housmg 114 which, as shown, may be elliptical in form with the longest axis extending longitudinally of the body; and such shell or housing may contain such of the operative features of the airship as may be desired. The lateral supporting members E, one at each side of the body F, are rotatably mounted upon a common shaft 115 extending transversely of the body, or said shaft may be divided into two parts if desired. l

The axis of rotation of each of said aeroplanes .7b is preferably farther toward a forward edge portion 116 of such aeroplane than toward the rearward edge portion of the same. p designates operative connections between the aeroplanes 71., and Said opera- 40 pendence of all of the aeroplanes c throu hmovements of the .slidable shafts 117, one at each and the adjacent end of the respective shaft with an upwardly directed arm 123, lat the inner end portion of such aeroplane; andv between the upper end of-each of saidarms 117 extends a connecting rod 124,'which is pivotally connected with the res ective arm at one end, as at A125, and pivota y connected with the respective shaft 1-17 at the other end, as' at 126.. f

- The operation, vmethod of'use and advantages of the improvements-in'airshi s constitutingtheinvention will be rea y understood from the foregoing description,

taken in connection with the accompanying.

drawings and the following statementzln the 'flight of theairship, the aeroplanes c' vsustain the entirety in'the supporting meair, their-V dium, namely thel surrounding normal inclination-with respect totlie horizontal transverse plane of the airship presenting resistance. to the air', as required.

This normal inclination of all of tlie ae roplanes is'capable of Variation, by variation of the normal relative positions of the pistons 14 and 15 within `the cylinder 1l, which is accomplished by the controlhng means m acting upon the piston to' vary the height. of the column of liquid in the .cylinder .12.

Itis manifest'that, because of the inter-dethe agency of the operative connections4 and the' controlling means C, thatany variationin the status or condition ofthe atmosphere supporting the airship, and affecting-- any one of the aeroplanes 0, will afl'ect each of the other aero lanes c; and will so affect each and all of t e other aeroplanes e as to cause a compensation, throughout. the whole series of aeroplanes, with relation t o the disturbance or interruption of .stability pro- I' duced by such .variation inworkin or supporting conditions; for instance, 1 f a puii` of air of accelerated motion strikes the downwardly-inclined aeroplane c at the uper righthand corner of Fig. 4, and is deected therefrom, the lpiston rod 38 connected therewith will-be moved forwardly or outwardly, the pistonrod 39 connected' l with the aeroplane c at the lower right hand corner of Fig, 4, will be moved inwardly through 'the agency ofthe connecting lever 42, acting upon the outer end of the piston rod 16 as a. center. The piston`- rod '16 will be forced outwardly, forcing the4 piston 15 outwardly, and forcing the rod 40 and 41 inwardly in the manner to the member piston 14 inwardly through the medium of l the liquid in the cylinder 11. The liquid within the cylinder ll'will be redistributed accordingly, accommodating the-said movements of said pistons. The piston rod 17 will be moved forwardly,

necting lever 50, and increasing the angularity or inclination of the rearward aeroplanes e, until the wind pressure is equal on all` four planes. These series of operations and actuatio'ns will cause'a 'restablishment of stability or equilibrium of the moving thepiston through ythe conairship. The tendency of the airship -to rock or tilt laterally because of the increased pressure upon'the forward left -hand aero-'- ',plane4 c, engaged by a puff of air, will .be

counteracted by the increase-of inclination 1 [of the forward .l'ighthandaeroplane 0, and

the increased' resistancethereof to the air.

The increase of inclination of both rearward aeroplanes will' counteract the tendency ofthe forward end portion of the airship to. soar or riseunder-'thepressure of a puff of air upon the forward left handfaeroplane4 and because .of the increased resistance afforded by the increased inclination of the forward right .hand aeroplane. Vary'- ving eii'ectsA 'produced by variations. ofv atmospheric'conditions and airand air pressures `upon others of the four 'aeroplanes of the forward and rearward pairs, will, 11i

means a'nd the operative connections D 'to establish-and maintain stability and equilibrium ofthe entire airship.

The abdve description of operation has lbeen with respect to the' member or or anuch pistons' 31 to 34, inclusive, within the cylinders 26 to 29, inclusive, as accompany the movements of the piston rods 38'to 41, inclusive, as abovedescribed, will be idleiin .their effect with relation to the member or organism a.v The movements of ism `ai of the controlling means C.

lmanifest varying-'manners aii'ect all of the y fourv aeroplanes, through the controllingI such latter-pistons; under positive actuation ororganism b of the controlling means C, are caused in 'the following manner :-The in all lateral of, is `constantly rotated by the voperating means -o. Ifthe stability or equilibrium 'of the entire`airship be. disturbed,or interrupted, particularly by shifting of the load of the body A, the gyroscope g still maint-ains its vertical tends to maintain such4 shaft 110 'extends vertically. When the bodyA is tilted in any directionso as to position substantially, or. osition, so that itsA predetermined with respect i gyroscope g is freeto gyrate directions upon its support or -seat 65, and the rotating element 109 thereleave the horizontal position, the gyroscope V g maintains -its vertical psitiomthere being howeve a relative movement between mally, the mutilated gear heads 102, are out.

of mesh with the -gears 108 orvthe pinions 106.A l]`wo of the 4pairs of arms 104 are made longer than the other pair of -arms .104 so as to permit freedom of play or gyration o f the gyroscope g and the proper meshing ofv the gear heads 102 with the gears 108 or pinions 106, as now being' described. Let it be assumed that the lower side of the body A,

[that is the side nearest to the right hand margin of the sheet, in Fig. 2, is slightly depressed, due to shifting of the load. This will throw the gear heads 102 of the arms 104 at the upper side of the body A'into mesh with the gears 108 associated therewith and cause the rotation of the shafts 77 of the latter so as to rotate the beveled' gears 73, at the upper corners of Figa 2, in -the direction denoted by the adjacent arrows, and so' as to cause the beveled gears 72 at the upper corners of Fig. 2, to rotate in the directions opposite to those denoted by the arrows adjacent thereto. The beveled ears 73 whichr likewise mesh with the veled gears 75 upon the shafts 77 will be operated in `each instance in the direction opposite that in which the opposed gears 72 rotate. Each'of the ratchets 80 fixed to the beveled gear 73 will be rotated to cause `tions of the cylinders 27 and 29.

th'epawls 90 to intermittently oscillate the collars A8 6 and the shafts 82, intermittently opening the valves 91' and intermittently admitting compressed air to the outer` end plprsprings 100 maintain the exhaust valves 97 closed, the pawls 89 passing inoperatively over the ratchets 79. When the ratchets 80 are turned so that the pawls 90 are engaged Y' with the elongated teeth 81 at the farther end of said ratchets, orthe ends opposite to those engaged bythe ratchets in Fig. l2, said elongated teeth tend .to maintain the valves 91 open, so that continuous pressure of air is admitted to the cylinders 27 and 29 through the connection pipes 62. The admission of air, in this intermittent manner to the outer ends of the cylinders 27 and 29 causes the pistons 32 and 34 :to move inwardly of the cylinders 27 v and 29 respectively, causing the piston rods 39 and 4 1 to increase the inclinations ofthe aeroplanes 10 at the lower side of the tilted body A, the increased resistance of such aeroplane to the air tending to right the body A or restore it to equilibrium. Through the connecting levers 42 and 50 the piston rods 38 and 40 are caused to move outwardly, and the inclinations of the aeroplanes 10 at the upper side ofthe body -A are decreased through the link arms 48. The decreased resistance toJ the air of the last mentioned aeroplanes supplements the action of the increased incli'nation' of the other pair of aeroplanes, tending to` right the tilted body A. As the body yA gradually rights, or is righted as above described, relative movement of the gyroscope g and the frame- A, the` gyroscopev tending to maintain its 'equilibrium or upright position causes a reverse.

movement of the shafts 77, the collars 87 being actuated intermittently through the pawls 89 and the gears 72 to intermittently open the exhaust yvalves 97.. At the same time the pawls 90 ride inoperatively over the ratch'ets .80, permitting 'the closing of the valves 91 under actuation of the springs 101. The air is thus gradually exhausted from the outer ends ofthe cylinders 27 and 29, and the aeroplanes 10 all reassume their normal relative. inclinations through the member or organism a in the manner above described. j

From the above it will be seen that variation in conditions of atmospheric pressure, as well as variations in center of gravity of the body A, inasmuch as the same affect the equilibrium of the body A, aremet and provided for by the organisms or members a and b ofthe controlling lmeans C; and that said members or organisms aI and Z) are inter-related in their functions and operations, to the end that a sensitive response of the controlling means C is made to any variation of conditions of stability or equilibrium aifecting the body A and its connected parts and members; the specific illustrations of operation above given being paralleled by correspondin Aoperations re. sulting Vfrom variations o the conditions of disturbances resupposed.

In the modigedform of construction loo shown in Fig. 5,v the operation is the same` as that above described with the exception of that of the lateral supporting members E. These supporting members lbeing interrelated and interoperative, 'through the connecting lever 120, it results, from their particular mounting and operative connection, that if a variation in atmospheric pressure affects one of the members E, so as to vary itsy inclination, the inclination of the opposite member E will be oppositely affected, through the slidable shafts 117 and the connecting rods 124, so that there will bea tendency topmaintain or restore stability, or equilibrium of the body F. rlhese members E have a compensating interrela tion automatically combining to act-for the maintenance or restoration of equilibrium.

I do not desire to be understood as limit-ing myself to the specific construction, provision, combination, -relative arrangement and association of parts', members and features shown and described;'but`reserve the right to vary the same, in adapting the improvements to varying conditions of use,

without departing from the spirit of the 5 invention and the term of the following claims.

Having thus described my invention, what I claim and desire to 'secure by Letters Patent is l. Improvements in airships, comprising a body provided with supporting members, and controlling means for said supporting members; said controlling means comprising separate members or organisms responsive respectively to variations otatmospheric tions in atmosphericorl organism responsive to'variation in posi-v tion of load. .A

3. Improvements in airships, comprising a body, supporting members for the-body, and controlling means for the supporting members; saidcontrolling means comprising separate members'or organisms responsive respectively to variation of atmospheric being inter-related.

ypressure and support of load; and said members or organisms of said controlling means 4. Improvements in airships,

a body, adjustable aeroplanes' for, the supportv of the'body, and controllingmeans for the aeroplanes including mechanism whereby bsaid aeroplanes are so inter-related that variation of atmospheric pressure upon one 40 -of 'said aeroplanes causes variation of inclination of another of said aeroplanes.

5. Improvements 1n airships, comprlslng a body, adjustable aeroplanes for the sup port of the body,- and controllingl meansfor t5 the aeroplanes including mechanism whereby said aeroplanes are so inter-related that.

variation of atmospheric' pressure upon -one of said. aeroplanes causes variation of in clination of the1 others of said aeroplanes.

mprovements in airships, comprising ya body provided with a plurality of adjustably supporting aeroplanes; and controlling means including mechanism whereby said aeroplanes are so inter-related that variation 55. of atmospheric pressure upon one of said aeroplanes causes variation of inclination of the others ofsaid aeroplanes; said controlling means comprising'a plurality of pistons and a mobile medium affected by said pistons.

7. Improvements in airships, comprising a body provided with a plurality of adjustably supporting aeroplanes; and controlling 6'5 means including mechanism whereby [said aeroplanes are so inter-related that .variation the a ency comprising ,load of the body;

' air from the cylinder,

of atmospheric pressure upon one of Vsaid of pistons, a cylinder adapted to contain a mobile medium forming a connection beand means for varying vtween said pistons, the relative 'positions of said pistons.

8. Improvements 'in airships, comprising a body provided with a plural-ity of adjustably supporting aeroplanes; andcontrolling means includingmechanism whereby said aeroplanes are so inter-related that variation of atmospheric pressure upon one of said aeroplanes causes -variation of inclination of the'others of'said aeroplanes; said controlling means a-lso comprising a'plurality of pistons, a cylinder adapted'to contain a mobile medium forming a connection be- -tween said pistons; and 'means for va the relative positions' of said of said mobile medium. 9. mprovements in airships comprising a ,body provided with a plurality of supporting adjustably inter-relatedaeroplanes; and controlling Ameans for said aeroplanes responsive to variation of atmospheric. prespistons through sure; said controlling means also comprisp ing a cylinder, a plurality of pistons within said cylinder and provided each with a piston rod, and connecting levers carried by said-piston rods and connected respectively with saidaeroplanes.

10. Improvements in airships, comprising a body; a plurality of adjustable inter-related `aeroplanes for the supplort of the body; and controlling means for t e aeroplanes responsive to variation of the position of the comprising a 'plurality of cylinders, a'plu'- 'rality of pistons respectively in said cylinders and respectively operatively connected with said aeroplanes, pneumatic means, and gyroscopic means controlling said pneumatic means with respect to the admission of compressed air to -and exhaust of compressed air from said cylinders. 11; In improvements in airships, an ad justably supported aeroplane, a cylinder, a piston inthe 'cylinder voperatively connected with the aeroplane, 'a compressed air supply, valve means controlling the admission of compressed air to the cylinder, valve means controlling the exhaust of compressedand means controlling' both said valve means; and said last named means permitting intermittent admission of 'air toand exhaust from said cylinder.'

said controlling means assess air from the cylinder, and gyros'copic means controlling both said valve means; and said last named means permitting intermittent admission of air to and exhaust` from said cylinder.

- l13. Improvements 1n airships, comprising a body, a plurality of adjustable members disposed for resistance to atmospheric pressure, and controlling means for said mem? bers; said controlling means comprising separate members or organisms responsive respectlvely to varlatlon -of atmospheric pressure and imposition of Welght of load; and

said members or organisms of said control- A ling means beinginter-related.

l5. Improvements in airships, comprising a body, adjustable members disposed for resistance to atmospheric pressure, and mechanism vwhereby said members are so interrelated that variation of atmospheric pressure upon one of said members causes varia- 1tgion of inclination of another of said memers.

16. Improvements in airsliips, comprising 'a body, adjustable aeroplanes eccentrically connected with the body, and mechanism whereby said aeroplanes are so inter-related that variation of atmospheric pressure upon one of said aeroplanes causes variation of inclination of another of said aeroplanes.

In testimony whereof, I have signed my name to this specification, in the presence of two subscribing Witnesses.

JAMES J. ysLAvIN.

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